GB1516460A - Vane assembly for close coupling the compressor turbine and a single stage power turbine of a two-shaft gas turbine engine - Google Patents

Vane assembly for close coupling the compressor turbine and a single stage power turbine of a two-shaft gas turbine engine

Info

Publication number
GB1516460A
GB1516460A GB52761/76A GB5276176A GB1516460A GB 1516460 A GB1516460 A GB 1516460A GB 52761/76 A GB52761/76 A GB 52761/76A GB 5276176 A GB5276176 A GB 5276176A GB 1516460 A GB1516460 A GB 1516460A
Authority
GB
United Kingdom
Prior art keywords
turbine
vane
extension piece
stator vane
shroud
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
GB52761/76A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
CBS Corp
Original Assignee
Westinghouse Electric Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Westinghouse Electric Corp filed Critical Westinghouse Electric Corp
Publication of GB1516460A publication Critical patent/GB1516460A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1516460 Gas turbine plant with separate power turbine WESTINGHOUSE ELECTRIC CORP 17 Dec 1976 [23 Dec 1975] 52761/76 Headings F1G and FIT In a gas turbine engine comprising a compressordrive turbine 12a and a power turbine 14a, the gas flow duct therebetween is defined between an outer shroud 16 and an inner shroud 18, the duct being formed by arcuate segments of the shrouds each segment being formed integrally with two stator vanes 20 each of which terminates in a concave trailing edge surface 22. An angularly-movable stator vane 24 is associated with each stator vane 20, the leading edge of the movable stator vane co-operating with the concave surface 22 of the stator vane. A circular section seal member 50 is mounted in the concave surface to co-operate with the convex leading edge of the movable vane 24 so as to provide a gas-tight seal. Each movable stator vane 24 is formed with mounting pins at its ends, the radially outer pin 36 engaging within an aperture 34 formed in the outer shroud 16, a partspherical bearing 38 being provided. A control lever 70 is mounted so as to permit angular movement of the vane. The radially inner mounting pin 44 is received within an opening 42 formed in a shroud extension piece 32 which is secured to the downstream flange 30 of the inner shroud 18 by means of bolts 146 which pass through elongate holes 144 formed in the extension piece 32 and through openings in the flange 30. The extension piece 32 may be moved in a circumferential direction by means of a member (130) carrying an eccentric pin (132) which engages within a radial slot (122) formed in the forward face of the upstream flange of the extension piece 32, such adjustment correcting mis-alignment of the pivotable vane mounting bearings. The part-spherical bearing of the inner pin 44 is shown at 48.
GB52761/76A 1975-12-23 1976-12-17 Vane assembly for close coupling the compressor turbine and a single stage power turbine of a two-shaft gas turbine engine Expired GB1516460A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US05/643,718 US3990810A (en) 1975-12-23 1975-12-23 Vane assembly for close coupling the compressor turbine and a single stage power turbine of a two-shaped gas turbine

Publications (1)

Publication Number Publication Date
GB1516460A true GB1516460A (en) 1978-07-05

Family

ID=24581996

Family Applications (1)

Application Number Title Priority Date Filing Date
GB52761/76A Expired GB1516460A (en) 1975-12-23 1976-12-17 Vane assembly for close coupling the compressor turbine and a single stage power turbine of a two-shaft gas turbine engine

Country Status (6)

Country Link
US (1) US3990810A (en)
AR (1) AR211283A1 (en)
BE (1) BE849815A (en)
CA (1) CA1031267A (en)
GB (1) GB1516460A (en)
IT (1) IT1065526B (en)

Families Citing this family (54)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA1038298A (en) * 1975-10-14 1978-09-12 John Korta Adjustable vane assembly for a gas turbine
US4214852A (en) * 1978-04-20 1980-07-29 General Electric Company Variable turbine vane assembly
JPS54151741A (en) * 1978-05-22 1979-11-29 Toshiba Corp Multi-stage hydraulic machine
FR2556410B1 (en) * 1983-12-07 1986-09-12 Snecma DEVICE FOR CENTERING THE INSIDE RING OF A VARIABLE TIMING FINS STATOR
FR2582720B1 (en) * 1985-05-29 1989-06-02 Snecma PROCESS FOR PRODUCING A TURBOMACHINE BLADE PIVOT AND A STATOR BLADE COMPRISING SAME
FR2607188B1 (en) * 1986-11-26 1991-02-08 Snecma TURBOMACHINE INPUT CASING WITH RADIANT ARMS
US4834613A (en) * 1988-02-26 1989-05-30 United Technologies Corporation Radially constrained variable vane shroud
US6045325A (en) * 1997-12-18 2000-04-04 United Technologies Corporation Apparatus for minimizing inlet airflow turbulence in a gas turbine engine
GB2339244B (en) * 1998-06-19 2002-12-18 Rolls Royce Plc A variable camber vane
US6450763B1 (en) * 2000-11-17 2002-09-17 General Electric Company Replaceable variable stator vane for gas turbines
US20040120618A1 (en) * 2002-12-24 2004-06-24 General Electric Inlet guide vane bushing having extended life expectancy
US7121727B2 (en) * 2002-12-24 2006-10-17 General Electric Company Inlet guide vane bushing having extended life expectancy
FR2850131B1 (en) * 2003-01-17 2005-02-25 Snecma Moteurs ARRANGEMENT FOR MOUNTING AUBES WITH VARIABLE SHAFT
GB2402179B (en) * 2003-05-27 2006-02-22 Rolls Royce Plc A variable vane arrangement for a turbomachine
DE10352789B4 (en) * 2003-11-12 2006-04-13 Mtu Aero Engines Gmbh gas turbine
GB2411440B (en) * 2004-02-24 2006-08-16 Rolls Royce Plc Gas turbine nozzle guide vane
EP1831521B1 (en) * 2004-12-01 2008-08-20 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
FR2908828B1 (en) * 2006-11-16 2013-11-01 Snecma DEVICE FOR SEALING MOBILE WHEEL SENSE FOR TURBOMACHINE INPUT DIRECTOR WHEEL
US7862296B2 (en) * 2007-08-24 2011-01-04 Siemens Energy, Inc. Turbine vane securing mechanism
US8202043B2 (en) * 2007-10-15 2012-06-19 United Technologies Corp. Gas turbine engines and related systems involving variable vanes
US9249736B2 (en) * 2008-12-29 2016-02-02 United Technologies Corporation Inlet guide vanes and gas turbine engine systems involving such vanes
US8439635B2 (en) * 2009-05-11 2013-05-14 Rolls-Royce Corporation Apparatus and method for locking a composite component
FR2948965B1 (en) * 2009-08-06 2012-11-30 Snecma RECTIFIER STAGE FOR A TURBOMACHINE
US8534991B2 (en) * 2009-11-20 2013-09-17 United Technologies Corporation Compressor with asymmetric stator and acoustic cutoff
DE102010014900A1 (en) * 2010-04-14 2011-10-20 Rolls-Royce Deutschland Ltd & Co Kg Secondary flow channel of a turbofan engine
DE102010021145A1 (en) * 2010-05-21 2011-11-24 Mtu Aero Engines Gmbh Adjustable guide vane and turbomachine
US8668445B2 (en) * 2010-10-15 2014-03-11 General Electric Company Variable turbine nozzle system
US20120163960A1 (en) * 2010-12-27 2012-06-28 Ress Jr Robert A Gas turbine engine and variable camber vane system
US9309778B2 (en) * 2010-12-30 2016-04-12 Rolls-Royce North American Technologies, Inc. Variable vane for gas turbine engine
US20120275922A1 (en) * 2011-04-26 2012-11-01 Praisner Thomas J High area ratio turbine vane
US9062559B2 (en) * 2011-08-02 2015-06-23 Siemens Energy, Inc. Movable strut cover for exhaust diffuser
US8480423B2 (en) * 2011-08-16 2013-07-09 Tyco Electronics Corporation Contact region of an electrically conductive member
US8920116B2 (en) * 2011-10-07 2014-12-30 Siemens Energy, Inc. Wear prevention system for securing compressor airfoils within a turbine engine
US9074489B2 (en) * 2012-03-26 2015-07-07 Pratt & Whitney Canada Corp. Connector assembly for variable inlet guide vanes and method
US20140314549A1 (en) * 2013-04-17 2014-10-23 General Electric Company Flow manipulating arrangement for a turbine exhaust diffuser
EP3030756B1 (en) * 2013-08-07 2020-04-29 United Technologies Corporation Variable area turbine arrangement for a gas turbine engine
US11118471B2 (en) * 2013-11-18 2021-09-14 Raytheon Technologies Corporation Variable area vane endwall treatments
EP2905425B1 (en) * 2014-02-06 2019-07-10 United Technologies Corporation Variable vane and seal arrangement
EP2960437B1 (en) * 2014-06-26 2018-08-08 MTU Aero Engines GmbH Variable guide vane device for a gas turbine and gas turbine equipped with such a device
US9617864B2 (en) * 2014-07-21 2017-04-11 United Technologies Corporation Seal assembly for a guide vane assembly
US9995166B2 (en) * 2014-11-21 2018-06-12 General Electric Company Turbomachine including a vane and method of assembling such turbomachine
DE102014223975A1 (en) * 2014-11-25 2016-05-25 MTU Aero Engines AG Guide vane ring and turbomachine
US9879560B2 (en) 2015-05-15 2018-01-30 United Technologies Corporation Vane strut positioning and securing systems
US10626739B2 (en) * 2015-10-27 2020-04-21 Mitsubishi Heavy Industries, Ltd. Rotary machine
EP3421754B1 (en) * 2016-03-30 2021-12-01 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Variable geometry turbocharger
DE102016208154A1 (en) 2016-05-12 2017-11-16 MTU Aero Engines AG Inlet Grille for a Compressor, Compressor and Method of Making an Ingress Grille
DE102016208706A1 (en) * 2016-05-20 2017-11-23 MTU Aero Engines AG Guide vane for a Eintrittsleitgitter
US10662782B2 (en) * 2016-11-17 2020-05-26 Raytheon Technologies Corporation Airfoil with airfoil piece having axial seal
US10781707B2 (en) 2018-09-14 2020-09-22 United Technologies Corporation Integral half vane, ringcase, and id shroud
US10794200B2 (en) 2018-09-14 2020-10-06 United Technologies Corporation Integral half vane, ringcase, and id shroud
EP3650637B1 (en) * 2018-11-08 2021-10-27 Raytheon Technologies Corporation Gas turbine vane stage with half vanes integral with an outer case and an inner shroud
BE1027876B1 (en) * 2019-12-18 2021-07-26 Safran Aero Boosters Sa TURBOMACHINE MODULE
US11428113B2 (en) 2020-12-08 2022-08-30 General Electric Company Variable stator vanes with anti-lock trunnions
DE102022102421A1 (en) 2022-02-02 2023-08-03 MTU Aero Engines AG BLADE ASSEMBLY FOR A FLUID MACHINE

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1050166A (en) * 1952-06-04 1954-01-05 Linkage system
GB755527A (en) * 1953-10-15 1956-08-22 Power Jets Res & Dev Ltd Mounting of swivelling guide vane elements in axial flow elastic fluid turbines
GB774501A (en) * 1953-10-15 1957-05-08 Power Jets Res & Dev Ltd A stator guide vane construction for elastic fluid turbines
NL198161A (en) * 1955-06-17
GB946995A (en) * 1961-05-23 1964-01-15 Rolls Royce Fluid flow machine such as a gas turbine engine
DE1926338A1 (en) * 1969-05-23 1970-12-17 Motoren Turbinen Union Device for supporting pivotable guide vanes of thermal turbo machines
DE1931044A1 (en) * 1969-06-19 1971-03-11 Motoren Turbinen Union Guide grille for turbo machines with adjustable guide vanes
US3887297A (en) * 1974-06-25 1975-06-03 United Aircraft Corp Variable leading edge stator vane assembly

Also Published As

Publication number Publication date
CA1031267A (en) 1978-05-16
AR211283A1 (en) 1977-11-15
BE849815A (en) 1977-06-23
US3990810A (en) 1976-11-09
IT1065526B (en) 1985-02-25

Similar Documents

Publication Publication Date Title
GB1516460A (en) Vane assembly for close coupling the compressor turbine and a single stage power turbine of a two-shaft gas turbine engine
US4573866A (en) Sealed shroud for rotating body
US3999883A (en) Variable turbomachine stator
GB775454A (en) Improvements in or relating to engine supercharging device
US7458771B2 (en) Retaining of centering keys for rings under variable angle stator vanes in a gas turbine engine
EP2659112B1 (en) Gas turbine engine and variable camber vane system
GB1201949A (en) Movable stator vane unit for a bladed fluid flow machine
EP1122407A3 (en) Controllable guide vane apparatus for a gas turbine engine
GB1281786A (en) Turbine nozzles
US20220170381A1 (en) Variable guide vane assembly and vane arms therefor
GB1504463A (en) Adjustable vane assembly for a gas turbine engine
US3563669A (en) Variable area nozzle
GB790854A (en) Improvements in or relating to axial-flow fluid machines
GB1491556A (en) Rotor blades for turbomachines
US20220162958A1 (en) Variable guide vane assembly and bushings therefor
GB1266254A (en)
US11371369B2 (en) Vanes and shrouds for a turbo-machine
US3909155A (en) Sealing of vaned assemblies
JPS61192814A (en) Exhaust turbo overcharger for internal combustion engine
GB749577A (en) Improvements in or relating to blade ring assemblies for axial flow compressors or turbines
GB2061396A (en) Turbine blade tip clearance control
GB774501A (en) A stator guide vane construction for elastic fluid turbines
GB1317529A (en) Axial flow turbine structure
US2972441A (en) Variable blade system
GB1081943A (en) Improvements in stator assembly for turbines and compressors

Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee